MAE112HW3 - Due: January 30, 2009 MAE 112 Winter 2009...

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1 Due: January 30, 2009 MAE 112 Winter 2009 Homework Assignment #3 1. Consider a jet engine flying at a Mach number of 1.5. A normal shock sits at the entrance of the divergent diffuser. The diffuser entrance cross-sectional area is 3.0 ft 2 . The ambient conditions are 520 R for temperature and 1 atmosphere for pressure. (a) What is the stagnation pressure immediately behind the shock? What is the Mach number immediately behind the shock? What is the mass flow through the diffuser? (b) What is the minimum cross-sectional area required at the downstream end of the diffuser in order to insure that the Mach number of the flow there does not exceed 0.10? 2. Consider a Kantrowitz-Donaldson diffuser designed for a flight Mach number of 1.75. The entrance area equals 2.0 ft 2 and the ambient air temperature and pressure are 500 R and 0.8 atmosphere. The flow is isentropic everywhere except across the normal shockwave. Determine: (a) the minimum cross-sectional area of the throat such that a normal shock may be
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This note was uploaded on 03/10/2009 for the course MAE AE112 taught by Professor Sirgianno during the Spring '09 term at UC Irvine.

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MAE112HW3 - Due: January 30, 2009 MAE 112 Winter 2009...

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